RU2574565C1 - Power supply system of space vehicle with power regulation of solar panel by inverting-transformer converter - Google Patents

Abstract

FIELD: power industry.

SUBSTANCE: system contains a solar panel (SP) connected by busbars to a voltage regulator, wherein in positive busbar a current transmitter is installed; transformer, its primary winding is connected with the voltage regulator made as per bridge circuit of the inverter, rectifier, battery with charge monitoring device, load, charger and discharger, wherein it contains a control system with extreme step power regulator of the solar panel, that is connected by the measuring input with the current transmitter output, and by another measuring inputs with SP and load busbars with possibility of control of the voltage regulator transistors with input C-filter, wherein the secondary winding of the transformer is connected with the inputs of the rectifier containing output LC-filter, one its power outputs is connected with the charger input, discharger output and load input, the charger output is connected with the discharger input, and one battery terminals, the rectifier second output is connected with another battery terminal and load output, and battery measuring outputs are connected with the measuring inputs of the battery charge monitoring device.

EFFECT: increased power effectiveness of the system due to implementation of the extreme power regulation of the solar panel both under battery charge mode, and under mode of simultaneous power supply from solar panel and battery, as well as possibility of the solar panel use with work voltage both higher and lower voltage of battery and load.

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Description

The invention relates to the field of converting technology, in particular to onboard power supply systems (BOT) of spacecraft (SC), and can be used in the design and construction of power systems for automatic spacecraft based on solar and storage batteries (SB and AB).

The technical result of the invention is to increase the energy efficiency of the spacecraft’s power supply system through the implementation of extreme power control (ERM) of solar batteries both in the battery charge mode and in the mode of joint supply of onboard load from the SB and the battery, as well as the possibility of using a solar battery with operating voltage both above and below the voltage on the battery and on the load.

A widely known power supply system [1] with extreme power control of a photovoltaic battery, comprising a photovoltaic and storage batteries, a series voltage regulator (LV) for supplying a load from a photovoltaic battery, a charging and discharge device (charger and switchgear). Extreme regulation of the power of the photovoltaic battery is carried out by the charger when the load is powered and the battery is simultaneously charged, as well as by a voltage regulator while the load is powered from the SB and AB. The power supply system with a photoelectric battery is designed to form a power low-voltage (27-28 V) load power bus.

The disadvantage of this power supply system is that the operating voltage of the solar battery must always be greater than the voltage of the load power bus. When creating high-voltage SEP spacecraft (100 V), the maximum value of the open circuit voltage of “cold” silicon SBs at the moments of spacecraft exit from the shadow areas of the Earth can reach 300 V, and for SBs made on the basis of gallium arsenide three-stage photoconverters, it can reach 210-220 V, which is unacceptable due to the possibility of electrostatic discharges occurring under vacuum conditions between the chains of SB photodiodes or current collector elements. To limit the voltage on the SB requires the use of special devices or the implementation of the operation modes of the BOT, limiting the voltage increase on the cooled SB no more than 180 V.

Currently, the design of high-voltage high-voltage Russian and foreign BOTS automatic spacecraft operating in a geostationary orbit is based on gallium arsenide three-stage photoconverters and shunt voltage regulators SB [2], limiting the voltage on the SB at the voltage level of the load power bus (100 V), and therefore not allowing to implement the ERM SB mode. During the entire period of active operation, the solar battery is significantly underused in energy, since the optimal voltage values at which the SB generates a maximum of power significantly exceed the stabilized voltage of 100 V.

The aforementioned problems of inefficient use of SB in energy and a possible increase in voltage above 180 volts can be solved by using inverter-transformer energy conversion circuits that allow you to arbitrarily coordinate the operating voltage ranges on the SB, AB and on the load and implement the SB ERM mode as in the AB charge mode, and in the mode of joint supply of onboard load from SB and AB. When using them, the voltage on the solar battery can be both higher and lower than the voltage at the load.

Closest to the technical nature of the claimed invention is the power supply system of the spacecraft described in the patent [3] (Fig. 1).

The power supply system consists of a solar battery 1, a battery 2, a voltage stabilizer for a solar battery 3, a discharge device for a battery 4, a battery charger 5, an extreme power regulator for a solar battery 6, a current sensor for a solar battery 7, a transformer 8, and primary transformer 9 windings , 10, secondary windings of the transformer 11, 12, 15, 20, power devices 13, 16, 18 loads of direct or alternating current 14, 17, 19, control circuits 21 transistors 22-25 voltage stabilizer 3, control circuits 26 transistors 27-30 bit device 4.

The power supply system operates as follows.

When the power of SB 1 exceeds the total power consumed by loads 14, 17, 19 (power supply of loads from SB) by voltage stabilizer 3, a stable voltage is maintained using the feedback of device 18 on the secondary winding 20 of transformer 8. On the secondary windings 11, 12, 15 of the transformer 8, a stable voltage is also maintained taking into account the transformation ratios of the windings. At the same time, AB 2 is charged, memory 5, RU 4 and SB 6 are shut off.

When the battery is charged, the charger 5 is turned on. The signal on the inclusion of the charger 5 is fed to the input of the ERM 6. As a result, the ERM mode of SB 1 is realized. At the same time, the RU 4 is disabled.

When the load is supplied from the battery and the power of SB 1 is equal to zero, the switchgear 4 is connected, the voltage is stabilized at the secondary winding 20 of the transformer 8 using the feedback of the device 18. In this case, the voltage stabilizer 3, ERM 6, memory 5 are disabled.

When the load is supplied together from the SB and AB, the voltage on the secondary winding 20 of the transformer 8 is stabilized by the RU 4, which compensates for the lack of power generated by the SB. The voltage on the SB is determined by the voltage level of the battery, since the SB and the battery in this mode are connected in parallel through the transformer, this eliminates the possibility of regulating the voltage on the SB and, accordingly, the implementation of the extreme power control mode of the SB. The power generated by the SB will be determined in this case by the voltage of the AB, reduced to the SB through the transformation coefficient specified during the design.

Thus, the power supply system [3] cannot carry out the extreme power control mode of the power supply in the mode of joint power supply of the load from the power supply and the power supply, which is its main drawback. Another disadvantage is the low coefficient of energy transfer to the load through the battery.

The aim of the invention is to increase the energy efficiency of the SEP spacecraft by implementing extreme control of the power of the SB both in the charge state of the battery and the discharge of the battery (while supplying the load from the SB and battery), as well as providing the possibility of using a solar battery with an operating voltage of both higher and lower than the voltage on the battery and on the load, and thereby eliminating the possibility of increasing the open circuit voltage of the cooled SB at the moments when the spacecraft leaves the Earth’s shadow more than 180 volts.

In FIG. 2 is a functional diagram of the inventive power supply system of a spacecraft with solar power control by an inverter-transformer converter, which contains a solar battery 1, a current sensor 2, a control system 3 with an extreme step power regulator SB, a voltage regulator 4, made in the form of a bridge inverter with input C-filter, transformer 6 with primary winding 5 and secondary winding 7, rectifier 8 with output LC filter, device for monitoring the degree of charge (UKZB) AB 9, s a battery device 10, a battery 11, a discharge device 12, and a load 13.

The solar battery 1 is connected by positive and negative buses to the voltage regulator 4, and the current sensor 2 is installed in the positive bus 2. The output of the voltage regulator 4 is connected to the primary winding 5 of the transformer 6. In this case, the control system 3 is connected by a measuring input to the output of the current sensor 2, and other measuring inputs with power buses SB 1 and load 13. Signals from the current sensor 2 and power buses SB 1 are used to calculate the power generated by SB 1.

The transistors of the inverter of the voltage regulator 4 are controlled by the control system 3 according to a predetermined algorithm in accordance with the zone principle of regulating the voltage of SB 1 and load 13 (Fig. 3). The inputs of the rectifier 8 are connected to the secondary winding 7 of the transformer 6. The input of the charger 10 and the output of the discharge device 12 are connected to one of the outputs of the rectifier 8 and the load input 13. The battery 11 of one of its power terminals is connected to the output of the charger 10 and the input of the discharge device 12. The second output of the rectifier 8, the second power terminal of the battery 11 and the output of the load 13 are connected to a common bus power supply load 13. The measuring outputs of the battery 11 are connected to the measuring inputs charge level control devices AB 9, an information signal from UKZB 9 is transmitted to the charger 10.

The power supply system of the spacecraft operates in the following modes.

1. The load power is less than the power generated by the SB (P _N <P _SBmax ), the _battery is charged.

When the battery is charged 11, the charger 10 is disconnected. The inverter 4 stabilizes the voltage on the winding 5 of the transformer 6, corresponding to the voltage on the load 13 in its upper subband (Fig. 3) according to the signals of the control system 3, which uses the feedback voltage (voltage of the load supply bus).

2. The load power is less than the power generated by the SB (P _N <P _SBmax ), the _{battery is} discharged.

Upon receipt of a signal from UKZB 9 about the need to charge the battery 11, the charger 10 is turned on, which starts to open and direct the current to the battery 11. If the total value of the battery power is AB 11 (the memory 10 operates in current limiting mode) and the load power 13 is less than the maximum power value generated by SB 1, then the operation mode corresponds to mode 1 described above. In this case, the charge power of the battery 11 is an additional load that does not change the mode of operation of the EPA. The voltage at the load 13 is regulated in the upper sub-range (Fig. 3).

If the total value of the charge power AB 11 and the load power 13 is greater than the maximum value of the power generated by SB 1, then the voltage on the power supply bus load 13 is reduced to the control sub-range of the charger 10. Charger 10 begins to limit the charge current of AB 11, thereby stabilizing the output BOT voltage (Fig. 3).

As soon as the voltage on the load power bus 13 falls below the control sub-range of the inverter 4, the control system 3 puts the inverter 4 into the voltage control mode SB 1 according to the control signals from the step extreme controller (ESR), which is part of the control system. ESR, multiplying the signals of the current sensor 4 and voltage from SB 1, calculates the current value of the power generated by the solar battery 1, and step by step changing the voltage value SB 1 in the search range of the extremum (Fig. 3), it finds the optimal voltage value SB 1.

Thus, the inverter 4 provides maximum power from SB 1, and the charger 10 stabilizes the output voltage, sending all the excess power of SB 1 to the charge of AB 11.

3. The load power is greater than the power generated by the SB (P _N > P _{SB max} ), discharge AB. Power supply from SB and AB.

When the load power of 13 increases to a value greater than SB 1 can generate in the extreme power control mode (P _N > P _{SB ERM} ), the battery 11 stops, the charger 10 closes. The voltage on the power bus load 13 is reduced to the control sub-range RU 12 (Fig. 3), the discharge device 10 begins to adjust the output voltage in its (lower) sub-range, making up for all the lack of power in the load 13.

The operating mode of the inverter 4 does not change; it still regulates the voltage of SB 1 in the region of the power extremum according to ESR signals.

When the load power of 13 decreases to values less than that generated by SB 1 in the ERM mode (P _N <P _{SB ERM} ), the discharge of AB 11 stops, the voltage on the load power bus rises to the control sub-band of memory 10 (Fig. 3), which again will begin to regulate the output voltage, sending all the excess power of SB 1 to the charge of AB 11.

4. The solar battery does not generate power (P _SB = 0), battery discharge.

When the SC enters the Earth’s shadow or the flaps of the SB 1 panels from the Sun, the solar battery 1 does not generate power (P _SB = 0). The voltage on the load power bus 13 is reduced to the control sub-range of RU 12 (Fig. 3), the discharge device 12 begins to regulate the output voltage in its (lower) sub-range, making up for all the lack of power in the load 13. The inverter 4 is in standby mode.

Thus, in the claimed circuit, the voltage of SB 1 can be regulated in a wide range, including the point ΒΑΧ SB 1 with maximum power, both in the charge mode of the battery 11 and in the power mode together from SB 1 and battery 11, which increases the energy efficiency of the solar cell .

In the BOT, performed according to the developed scheme based on inverter-transformer energy conversion of SB 1, the operating voltage ranges for SB 1, AB 11 and load 13 are quite simply coordinated by changing the voltage transformation coefficient of the SB and the operating conditions of the solar battery. The voltage on the solar battery 1 can be both higher and lower than the voltage on the load 13. The solar battery 1 can be designed to exclude the possibility of increasing its open circuit voltage above a predetermined value (above a critical value of 180 V).

An increase in the energy efficiency of the BOT of the spacecraft according to the proposed scheme is also achieved by reducing energy losses during its transfer from the SB to the load through the AB, since instead of an inverter-transformer converter operating as a discharge device, a boost DC-DC converter with a higher efficiency is used .d.

Used sources

1. Pat. RF №2101831, H02J 7/35. Power supply system with extreme power regulation of a photovoltaic battery / K.G. Gordeev, S.P. Cherdantsev, Yu.A. Shinyakov. Application No. 95119971 dated 11/27/1995. Publ. 01/10/1998, Bull. No. 1.

2. Power supply systems for large platforms in geostationary orbit / V.V. Khartov, G.D. Evenov, B.C. Kudryashov, M.V. Lukyanenko // Electronic and Electromechanical Systems and Devices: Sat. scientific tr - Novosibirsk: Nauka, 2007 .-- S. 7-16.

3. Pat. RF №2396666, H02J 7/34. Spacecraft power system. / B.C. Kudryashov, V.O. Elman, M.V. Nesterishin, K.G. Gordeev, V.N. Gladushenko, V.V. Khartov, S.G. Kochura, V.G. Soldatenko, N.V. Melnikov, R.V. Kozlov Application No. 2009124704 from 06/29/2009. Publ. 08/10/2010, Bull. Number 24.

Claims (1)

The power supply system of the spacecraft, consisting of a solar battery connected by its positive and negative power buses to the voltage regulator, and in the positive bus there is a current sensor, a transformer, the primary winding of which is connected to the voltage regulator, built on the bridge circuit of an inverter, rectifier, battery with a device for controlling the degree of charge, load, charging and discharge devices, characterized in that it contains a control system with extreme step regulation a power generator of the solar battery, which is connected by the measuring input to the output of the current sensor, and by other measuring inputs, with the power buses of the solar battery and the load with the possibility of controlling the transistors of the voltage regulator with an input C-filter, and the secondary winding of the transformer is connected to the inputs of the rectifier containing the output LC filter, one of the power outputs of which is connected to the input of the charger, the output of the discharge device and the input of the load, the output of the charger is connected to the input of the discharge the nuclear device and one of the power terminals of the battery, the second power output of the rectifier is connected to the other power terminal of the battery and the load output, and the measuring outputs of the battery are connected to the measuring inputs of the device for monitoring the state of charge of the battery, the information signal from which is transmitted to the charger.

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